BR102021000478A2 - METHOD OF CHANGING A BUMPER CURVE OF AN IMPACT BUMPER ASSEMBLY, METHOD OF SELECTING A BUMPER SETTING OF AN IMPACT BUMPER ASSEMBLY FOR AN AIRCRAFT, AND, IMPACT BUMPER ASSEMBLY - Google Patents

Abstract

method of changing a damping curve of a shock absorber assembly, method of selecting a damping setting of a shock absorber assembly for an aircraft, and, shock absorber assembly. a damping actor selector may be configured to transition a multi-actor damping system from a first damping actor configuration to a second damping actor configuration. the multi-actor damping system can be used in a shock absorber assembly to change a shock absorber assembly's damping curve. the damping actor selector can be coupled to a measuring pin of a shock absorber assembly. the damping actor selector can be configured to rotate the metering pin to transition the multi-actor damping system from a first damping actor setting to a second damping actor setting. the first damping actor configuration may correspond to a first damping curve. the second damping actor configuration may correspond to a second damping curve. the first damping curve being different from the second damping curve.

Description

METHOD OF CHANGING A BUMPER CURVE OF AN IMPACT BUMPER ASSEMBLY, METHOD OF SELECTING A BUMPER SETTING OF AN IMPACT BUMPER ASSEMBLY FOR AN AIRCRAFT, AND, IMPACT BUMPER ASSEMBLY FIELD OF THE INVENTION

[001] The present disclosure relates generally to a multi-actor damping system and, more particularly, to a multi-actor damping system for use in a landing gear system.

FUNDAMENTALS OF THE INVENTION

[002] Impact absorbing devices are used in a wide variety of vehicle suspension systems to control the movement of the vehicle and its tires relative to the ground and to reduce the transmission of transient forces from the ground to the vehicle. Impact absorbing shock absorbers are a common component in most aircraft landing gear assemblies. Impact dampers control the movement of the landing gear and absorb and dampen loads imposed on the landing gear during landing, taxiing, braking and taking off.

[003] An impact cushion generally performs these functions by compressing a fluid within a sealed chamber formed by hollow telescopic cylinders. Fluid generally includes both a gas and a liquid, such as hydraulic fluid or oil. One type of shock absorber generally uses an “air over oil” arrangement in which a confined gas volume is compressed as the shock absorber is compressed axially and an oil volume is measured through an orifice. The gas acts as an energy storage device, similar to a spring, so that after a compressive force has ended, the shock absorber returns to its original length. Impact dampers also dissipate energy by passing oil through the orifice so that as the impact absorber is compressed or extended, its rate of movement is limited by the damping action from the interaction of the orifice and oil.

SUMMARY

[004] A method for changing a damping curve of an impact damper assembly is disclosed in this document. The method may comprise: rotating, by means of a damping actor selector, a measurement pin from a standard position around a centerline of the measurement pin in a first direction, the standard position corresponding to a first configuration of damping actor; defining, by means of the damping actor selector, a first actor angle corresponding to a second damping actor configuration.

[005] In various embodiments, the first damping actor configuration may include a first damping curve, the second damping actor configuration may include a second damping curve, and the first damping curve and the second damping curve may be many different. The first damping curve can be for a conventional aircraft landing. The second damping curve can be for a catapult launch of the aircraft. The method may further comprise rotating, by means of the damping actor selector, the measuring pin from the first actor angle to a second actor angle. The second actor angle can correspond to the first damping actor setting. The second actor angle can correspond to a third damping setting. The first damping actor configuration may include a first damping curve, the second damping actor configuration may include a second damping curve, the third damping configuration may include a third damping curve, wherein the first damping curve is different from the second damping curve, where the second damping curve is different from the first damping curve and where the first damping curve is different from the third damping curve. The first actor angle can be a relative clock angle between the measuring pin and a support cylinder.

[006] A method for selecting a damping configuration of an impact damper assembly for an aircraft is disclosed in this document. The method may comprise: sending, by a controller, a catapult launch command to a launch bar lock and a damping actor selector; extending, by the controller, the launch bar latch to an aircraft deck to configure the aircraft for a catapult launch; transitioning, via the controller, the damping actor selector from a first damping actor configuration to a second damping actor configuration in response to the catapult launch command.

[007] In various embodiments, the first damping actor configuration may correspond to a first damping curve, the second damping actor configuration may correspond to a second damping curve, and the first damping curve and the second actor curve damping can be different. The method may further comprise transitioning the damping actor selector from the first damping actor configuration to the second damping actor configuration, further comprising setting an actor angle, where the actor angle is a clock angle between a measuring pin and a damper cylinder. The method may further comprise transitioning, via the controller, the damping actor selector from the second damping actor configuration to the first damping actor configuration in response to receiving a signal from a sensor that a wheel is not suffering a load. The method may further comprise sending, by the controller, a re-engagement command for locking the launch bar and the damping actor selector; and transitioning, via the controller, the damping actor selector from the second damping actor configuration to the first damping actor configuration in response to the re-engagement command.

[008] A shock absorber assembly is disclosed in this document. The snubber assembly may comprise: a snubber cylinder including a primary chamber; a snubber piston, the snubber cylinder configured to receive the snubber piston; an orifice support tube positioned within the primary chamber of the cushion cylinder; a main orifice assembly disposed within the orifice support tube, the main orifice assembly including a main orifice plate; and a measurement pin positioned within the primary chamber, the measurement pin defining an axis; and the damping actor selector configured to rotate around the main orifice plate and transitioning the shock absorber assembly from a first damping actor configuration to a second damping actor configuration.

[009] In various embodiments, the damping actor selector can comprise a hydraulic actuation or pneumatic actuation. The damping actor selector can comprise at least one of an electric step or a servo motor. The damping actor selector may comprise a piston head coupled to the measuring pin. The measuring pin can rotate in response to the piston head which moves linearly along the shaft. The first damping actor configuration may include a first damping curve, the second damping actor configuration may include a second damping curve, and the first damping curve may be different from the second damping curve.

[0010] The above features and elements may be combined in various combinations without exclusivity, unless expressly stated otherwise in this document. These features and elements, as well as the operation of the disclosed modalities, will become more evident in light of the following description and the attached figures.

BRIEF DESCRIPTION OF THE FIGURES

[0011] The subject matter of this disclosure is particularly highlighted and distinctly claimed in the concluding portion of the descriptive report. A more complete understanding of the present disclosure, however, can be better obtained by referring to the detailed description and claims when considered in connection with the figures, in which like numbers indicate like elements.

[0012] FIG. 1 illustrates an impact cushion assembly in accordance with various embodiments;
FIG. 2 illustrates a detail of an impact cushion assembly in accordance with various embodiments;
FIG. 3 illustrates a portion of an impact cushion assembly in accordance with various embodiments;
FIG. 4 illustrates a portion of an impact cushion assembly including flow restrictors in a retracted position;
FIG. 5 illustrates a portion of an impact cushion assembly including flow restrictors in an deployed position;
FIG. 6 illustrates a flow restrictor in accordance with various embodiments;
FIG. 7 illustrates an orbit cam according to various embodiments;
FIG. 8A illustrates a perspective and side view of a measuring pin, in accordance with various embodiments;
FIG. 8B illustrates a cross section of the measuring pin of FIG. 8A, according to various modalities;
FIG. 9A illustrates a portion of an impact cushion assembly in a bypass closed position, in accordance with various embodiments;
FIG. 9B illustrates a portion of an impact cushion assembly in a bypass open position, in accordance with various embodiments;
FIG. 10A illustrates a cross-section of a portion of an impact cushion assembly having a first cushioning actor configuration, in accordance with various embodiments;
FIG. 10B illustrates a cross-section of a portion of an impact cushion assembly having a first cushioning actor configuration, in accordance with various embodiments;
FIG. 11A illustrates a cross section of a portion of an impact cushion assembly having a first orientation, in accordance with various embodiments;
FIG. 11B illustrates a cross section of a portion of an impact cushion assembly having a first orientation, in accordance with various embodiments;
FIG. 12A illustrates a cross section of a portion of an impact cushion assembly having a second orientation, in accordance with various embodiments;
FIG. 12B illustrates a cross-section of a portion of an impact cushion assembly having a second orientation, in accordance with various embodiments;
FIG. 13A illustrates a cross-section of a portion of an impact cushion assembly having a third orientation, in accordance with various embodiments;
FIG. 13B illustrates a cross section of a portion of an impact cushion assembly having a third orientation, in accordance with various embodiments;
FIG. 14A illustrates a cross-section of a portion of an impact cushion assembly having a second cushioning actor configuration, in accordance with various embodiments;
FIG. 14B illustrates a cross-section of a portion of an impact cushion assembly having a second cushioning actor configuration, in accordance with various embodiments;
FIG. 15 illustrates a portion of a main orifice assembly with a main orifice plate, metering pin, and concealed flow restrictors, in accordance with various embodiments;
FIG. 16 illustrates an exploded view of a main hole assembly, in accordance with various embodiments;
FIG. 17A illustrates a portion of an impact damper assembly during compression of the damper, in accordance with various embodiments;
FIG. 17B illustrates a portion of an impact snubber assembly during snubber extension, in accordance with various embodiments;
FIG. 18 illustrates a portion of an impact cushion assembly in accordance with various embodiments;
FIG 19 illustrates a metering plate and metering pin assembly, in accordance with various embodiments;
FIG. 20 illustrates a portion of an impact cushion assembly, in accordance with various embodiments;
FIG. 21 illustrates a portion of an impact cushion assembly, in accordance with various embodiments;
FIG. 22 illustrates an aircraft control system, according to various modalities and
FIG. 23 illustrates a method of using a damping actor selector, in accordance with various embodiments.

DETAILED DESCRIPTION

[0013] The detailed description of examples of modalities in this document refers to the attached figures, which show examples of modalities by way of illustration. While these examples of modalities are described in sufficient detail to enable those skilled in the art to practice the disclosure, it should be understood that other modalities can be carried out and that logical changes and adaptations can be made to the design and construction in accordance with this disclosure and the teachings of this document without departing from the spirit and scope of the disclosure. Therefore, the detailed description in this document is presented for illustrative purposes only and not limitation.

[0014] A multi-actor damping system is disclosed. The multi-actor damping system can be used in an impact damper assembly to change a damping curve of the impact damper assembly. A “damping curve,” as disclosed in this document, is the relationship between the shock absorber damping and travel. A multi-actor damping system, as disclosed in this document, can be configured to change a damping curve by synchronizing a measurement pin and/or main orifice plate to multiple positions. In various embodiments, a measurement pin of an impact damper assembly can comprise a damping profile. A "damping profile" as disclosed in this document is a variable cross-sectional area of the measurement pin along its length to establish a respective damping curve associated with the measurement pin.

[0015] In various embodiments, an impact damper assembly may include a plurality of damping actor configurations. A "damping actor configuration" as disclosed in this document is any configuration of the impact damping assembly that produces a single damping curve. An impact cushion assembly main orifice assembly can be configured to produce any number of cushioning actor configurations. The main orifice assembly can be configured to add or subtract the flow of the damping profile in response to changing a position of the main orifice assembly and/or the measuring pin. The impact damping assembly may include multiple actor angles corresponding to a respective damping actor configuration. An “actor angle,” as disclosed in this document, is a relative clock angle between the measuring pin and a support cylinder. The Actor Angle determines which Actor Damping setting is active.

[0016] The multi-actor damping system uses the actor angle to add or subtract the flow area from the damping profile of the measuring pin and/or change a discharge coefficient. The system may allow selection of multiple predefined damping actor configurations. Cradle performance can be improved by allowing selection of a damping profile based on a particular aircraft activity (eg a landing damping actor, a catapult damping actor, a taxi damping actor, a short takeoff and vertical landing damping actor (STOVL), a percolation damping actor or the like.

[0017] Referring now to FIG. 1, an impact cushion assembly 100 for use in a landing gear system, in accordance with various embodiments, is illustrated. The shock absorber assembly 100 may comprise a shock absorber cylinder 110, a shock absorber piston 120, a gauge pin 140, an orifice support tube 150 and a main orifice assembly 160. The shock absorber piston 120 may be coupled. operatively to the damper cylinder 110 as described in this document. The damper cylinder 110 may be configured to receive the damper piston 120 in a manner that allows the two components to telescope together and absorb and/or dampen forces that are transmitted thereto. In various embodiments, a liquid, such as hydraulic fluid and/or oil, can be located within the snubber cylinder 110. A gas, such as nitrogen or air, can also be located within the snubber cylinder 110. The snubber cylinder snubber 110 and snubber piston 120 may, for example, be configured to seal such that fluid contained within snubber cylinder 110 is prevented from leaking as snubber piston 120 translates relative to snubber cylinder 110.

[0018] The shock absorber assembly 100 may comprise a primary low pressure chamber 130 in which oil and gas may mix. In this regard, a gas volume (also referred to herein as a primary chamber gas volume) 131 and an oil volume (also referred to herein as an oil volume) 133 may be contained in the primary chamber 130. A portion of the primary chamber 130 may contain the volume of gas of the primary chamber 131 and may be referred to as a primary gas chamber 132. Similarly, the portion of the primary chamber 130 that contains the volume of oil 133 may be referred to herein as a oil chamber 134. The dashed line 135 represents the level of the oil volume 133 or the interface between the oil chamber 134 and the primary gas chamber 132. In other words, the oil volume 133 may be located below the line dashed 135 and the gas volume of the primary chamber 131 may be located above the dashed line 135. In this regard, the interface between the oil chamber 134 and the primary gas chamber 132 may move with respect to the primary chamber 130 depending on theposition of the damper piston 120 relative to the damper cylinder 110.

The measuring pin 140 and the orifice support tube 150 can be positioned within the primary chamber 130. The measuring pin 140 can translate with the damper piston 120 relative to the main orifice assembly 160. In various embodiments , the measuring pin 140 can be configured to rotate about a centerline of the measuring pin 140. In various embodiments, the orifice support tube 150 can be configured to rotate about a centerline of the orifice support tube. orifice 150. By rotating the measuring pin 140 or the orifice support tube 150, the impact cushion assembly 100 can change from a first cushioning actor configuration to a second cushioning actor configuration.

[0020] In various embodiments, the impact damper assembly 100 further comprises a damping actor selector 170. The damping actor selector 170 is configured to rotate the measuring pin 140 relative to the damper piston 120. In several In embodiments, the damping actor selector 170 can be coupled to the orifice support tube 150 and configured to rotate the orifice support tube 150 relative to the measurement pin 140. The damping actor selector 170 can provide position control by direct drive, transmitted over a link or any other position control method known in the art. For example, damping actor selector 170 may comprise hydraulic or pneumatic actuation. In this regard, pressure can be used to drive a damping actor selector piston head 170 linearly along the centerline of the measurement pin 140. As the piston moves, it can cause the pin to measurement 140 rotates due to a screw-thread interface between the measurement pin 140 and the damping actor selector piston 170.

[0021] In various embodiments, external supply pressure can be applied by oil volume 133 in oil chamber 134 and automatically return the damping actor selector to a neutral or standard damping actor setting. The pressure can be set to translate the damping actor selector piston along the centerline of the gauge pin 140 to change the damping actor settings. This setting can provide an inherent safety feature of providing its own power source to return the mute actor selector 170 to a default mute actor setting.

[0022] In various embodiments, the damping actor selector 170 may comprise an electric stepper motor, servo motor or the like. A stepper motor can provide accurate angular positioning with an open loop design. A servo motor can produce an accurate position and/or can provide a closed loop system. The damping actor selector 170 can interface with an aircraft control system. The aircraft control system can be configured to control the damping actor selector 170 and/or changing the impact damper assembly from a first damping actor configuration to a second damping actor configuration.

[0023] Referring now to FIG. 2, detail A of the shock absorber assembly 100 of FIG. 1, in accordance with various embodiments, is illustrated. In various embodiments, the main orifice assembly 160 further comprises a main orifice plate 180. The main orifice plate 180 may be disposed in a recess of the orifice support tube 150. The main orifice plate is coupled to the first orifice restrictor. flow restrictor 162 and/or the second flow restrictor 164. The first flow restrictor 162 and the second flow restrictor 164 may each comprise an opening 165 extending through the flow restrictor and defining a fulcrum around which the first flow restrictor 162 and second flow restrictor 164 rotate. Main orifice plate 180 can be configured to rotate with measuring pin 140. For example, when measuring pin 140 is rotated, it transitions torque to main orifice plate 180 through interface 195 between an opening in the main orifice plate 180 and one side of the measuring pin 140. In various embodiments, the main orifice plate 180 can be configured to rotate with the orifice support tube 150 relative to the measuring pin 140.

[0024] In various embodiments, the main orifice assembly 160 further comprises a first orbit cam 167 and a second orbit cam 169. The first orbit cam 167 and the second orbit cam 169 may be configured to remain stationary as required. measuring pin 140 and main orifice plate 180 rotate. Each orbit cam is configured to guide a respective flow restrictor from a first damping actor configuration to a second damping actor configuration. For example, as the main orifice plate 180 rotates about the centerline of the measuring pin 140, a head portion of a respective flow restrictor is guided in a respective orbit cam. For example, the head portion 610 of the first flow restrictor 162 can be guided in a respective track or groove of the second orbit cam 169. The track or groove of the second orbit cam 169 can be configured to cause the first restrictor 162 Rotate around the fulcrum toward the measurement pin 140 or away from the measurement pin 140.

[0025] Referring now to FIG. 3, an exploded view of a main hole assembly 160, in accordance with various embodiments, is illustrated. In various embodiments, the main orifice assembly 160 further comprises a main orifice plate holder 182 and a main orifice plate retainer 184. The main orifice plate 182 assembly can be configured to allow the main orifice plate 180 be axially constrained and/or also allow the main orifice plate to rotate freely about the centerline of the gauge pin 140. In various embodiments, the main orifice plate retainer 184 is configured to retain the main orifice plate assembly 182 axially. For example, the main orifice plate holder 184 can couple to the main orifice plate holder 182 and hold the main orifice plate holder 182 in place.

[0026] In various embodiments, the main hole assembly 160 further comprises a first spring 192 and a second spring 194. Each spring may be coupled to a respective flow restrictor. For example, first spring 192 is coupled to first flow restrictor 162 and second spring 194 is coupled to second flow restrictor 164. Each spring can be configured to charge a respective flow restrictor against measurement pin 140 in a respective damping actor setting. Each spring may comprise a torsion spring or the like. For example, the first spring 192 may be configured to apply torque to the first flow restrictor 162 over the fulcrum defined by the opening 165 of the first flow restrictor 162 in a first dampening actor configuration. By doing this, a damping curve of the shock absorber assembly 100 can be changed.

[0027] In various embodiments, the main orifice plate 180 may further comprise a plate portion 185 and a plurality of lugs 186. The plurality of lugs 186 may extend axially from a surface of the plate portion 185. Each flow restrictor it can couple to a first and a second cam of the plurality of cams. For example, the first flow restrictor 162 can be coupled to the first ledge 187 and the second ledge 188 to form the plurality of ledges 186.

[0028] Referring now to FIG. 4, a cross-section of the main orifice assembly 160 in a first damping actor configuration, in accordance with various embodiments, is illustrated. In the first damping actor configuration, the first flow restrictor 162 and the second flow restrictor 164 can be fully retracted. "Fully retracted", as disclosed in this document, occurs when each flow restrictor is not in contact with the measuring pin 140. Although fully retracted, the first flow restrictor 162 and the second flow restrictor 164 have little or no effect on damping curve. In various embodiments, when the first flow restrictor 162 and the second flow restrictor 164 are retracted, the damping curve is based on a damping curve associated with a profile of the measurement pin 140.

[0029] Referring now to FIG. 5, a cross-section of the main orifice assembly 160 in a second dampening actor configuration, in accordance with various embodiments, is illustrated. In the configuration of the second damping actor, the first flow restrictor 162 and the second flow restrictor 164 can be fully deployed. "Fully deployed", as disclosed in this document, occurs when each flow restrictor is in contact with the measuring pin 140. Although fully deployed, the first flow restrictor 162 and the second flow restrictor 164 effect the damping curve and/ or provide improved damping over the first damping actor setting. In various embodiments, when the first flow restrictor 162 and the second flow restrictor 164 are used, the damping curve is based on a damping curve associated with the profile of the measuring pin 140, as well as a profile of the first flow restrictor. 162 and the second flow restrictor 164.

[0030] Referring now to FIG. 6, various views of a flow restrictor 600, in accordance with various embodiments, are illustrated. The first flow restrictor 162 and the second flow restrictor 164 may be in accordance with the flow restrictor 600. The flow restrictor 600 comprises a head portion 610 and a restrictor portion 620.

[0031] The head portion 610 comprises a first mating surface 612 and a second mating surface 614. The first mating surface 612 may be disposed opposite the second mating surface 614. The first mating surface 612 may be configured to coupling to a boss on the plurality of shoulders 186 of the main orifice plate 180 (as shown in FIG. 3). Likewise, second mating surface 614 may be configured to mate with a protrusion on the plurality of shoulders 186 of main orifice plate 180. Head portion 610 may further comprise an aperture 615 extending through head portion 610 from the first mating surface 612 to the second mating surface 614. In various embodiments, the opening 615 may act as a fulcrum for the flow restrictor 600. The head portion may further comprise a protrusion 618 extending from an outer surface 616 of the head portion 610. Protrusion 618 may be configured to rotate flow restrictor 600. For example, protrusion 618 may contact a respective orbit cam (e.g., first orbit cam 167 to first restrictor of flow 162) and/or the protrusion 618 may be guided by a track on an inner surface of a respective orbit during deployment and/or retraction of the restrictor flow 600.

[0032] In various embodiments, restrictor portion 620 may comprise a column 622 extending from head portion 610 to a rear end 629 of flow restrictor 600. In various embodiments, column 622 may define an arc or the like. Column 622 can be disposed between a first convex surface 621 and a second convex surface 623. Column 622, first convex surface 621 and second convex surface 623 can be configured to interact with a spline and/or groove disposed on the pin. measurement 140 (from FIG. 2) when flow restrictor 600 is in an implanted position. In various embodiments, column 622, first convex surface 621, and second convex surface 623 can define an outer surface of restrictor portion 620.

[0033] In various embodiments, the restrictor portion 620 may comprise a concave surface 625 disposed opposite the first convex surface 621 and the second convex surface 623. The concave surface 625 may include a first recess 626 disposed therein. First recess 626 can be configured to receive a spring. The first recess 626 may be disposed on a portion of the concave surface 625 and a portion of the head portion 610.

[0034] In various embodiments, front portion 610 may further comprise a second recess 619. Second recess 619 and first recess 626 may partially define a channel. The channel can be configured to receive a spring, according to various modalities.

[0035] Referring now to FIG. 7, an orbit cam 700, in accordance with various embodiments, is illustrated. In various embodiments, orbit cam 700 is semi-annular. The orbit cam may comprise a first mating surface 702 and a second mating surface 704. The first mating surface 702 may include a male fastener 703. The second mating surface 704 may include a female fastener 705. In various embodiments, the first mating surface 702 and the second mating surface 704 can both contain male fasteners or the first mating surface 702 and the second mating surface 704 can both contain female fasteners. By having a male fastener on one mating surface and a female mating fastener on a second mating surface, a first orbit cam can be coupled to a second orbit cam and either the first orbit cam or the second orbit cam may have the same geometry. For example, the first orbit cam 167 and the second orbit cam 169 may conform to the orbit cam 700.

[0036] The orbit cam 700 may further comprise a guide ramp 710 disposed on a radially inner surface 712 of the orbit cam 700. The guide ramp 710 may extend radially inward from the radially inner surface 712 from a first axial end and extends axially and circumferentially around the radially inner surface 712. With combined reference to FIGs. 6 and 7, guide ramp 710 may be configured to guide protrusion 618 of a head portion 610 of a flow restrictor 600. For example, guide ramp 710 may change an axial position of protrusion 618 and retract or deploy the restrictor flow 600.

[0037] The orbit cam 700 may further comprise an anti-rotation feature 720. The anti-rotation feature 720 may be disposed on a radially outer surface 722 of the orbit cam 700. The anti-rotation feature 720 may be a flat recess 724 disposed on the radially outer surface 722. The anti-rotation feature 720 can be configured to interface with a corresponding anti-rotation feature in the main orifice plate 182 assembly (as shown in FIG. 3).

[0038] In various embodiments, the orbit cam 700 comprises a proximal end 732 and a distal end 734 disposed distally in an axial direction from the proximal end 732. The orbit cam 700 may comprise a slot 736 disposed proximal to the distal end 734. Slot 736 can be configured to receive a tongue from a mating main hole plate (e.g., main hole plate 180). As such, the main orifice plate can rotate while the orbit cam 700 can remain stationary.

[0039] Referring now to FIG. 8A, a measurement pin 140 is shown, in accordance with various embodiments. Measuring pin 140 may comprise an elongate member 805 extending from a first end 801 to a second end 809 and defining a central axis. Elongate member 805 may include a quadrilateral cross section. In various embodiments, the quadrilateral cross-section can comprise a trapezoidal cross-section, a square cross-section, or the like. In various embodiments, first end 801 may comprise a quadrilateral cross section (e.g., a trapezoidal cross section, a square cross section, or the like). A square cross section can provide improved torque transfer properties. A trapezoidal cross section can provide protection against errors when mounting a main hole assembly. In various embodiments, referring now to FIG. 8B, a cross section along section line AA of measuring pin 140 is illustrated in accordance with various embodiments.

[0040] With combined reference now to FIGs. 8A and 8B, on a first side 802 of the quadrilateral cross-section of the measuring pin 140, the measuring pin 140 may comprise a first spline profile 810. In various embodiments, the first spline profile 810 may comprise a groove 812 disposed in the first side 802 of quadrilateral cross section. In various embodiments, the groove can be a V-groove, a V-groove with a thread, or the like. The first spline profile 810 may extend a length L1 of the measuring pin 140. The length L1 of the first spline profile 810 may correspond to a full stroke length of a buffer stroke for an impact buffer assembly (e.g. shock absorber assembly 100 of FIG. 1). In various embodiments, L1 may be between 75% and 95% of the length of the measurement pin 140. In various embodiments, the first flute profile 810 may be disposed on a third side 806 of the quadrilateral cross section of the measurement pin 140. Third side 806 may be opposite first side 802. Third side 806 may comprise a groove 832 in accordance with groove 812.

[0041] In various embodiments, on a second side 804 of the quadrilateral cross section of the measuring pin 140, the measuring pin 140 may comprise a second spline profile 820. The second side 804 may be adjacent to the first side 802 and the third side 806. In various embodiments, the second spline profile 820 may comprise a slot 822 disposed in the second side 804 of the quadrilateral cross-section. In various embodiments, the groove can be a V-groove, a V-groove with a thread, or the like. The second spline profile 820 may extend a length L2 of the measuring pin 140. The length L2 of the second spline profile 820 may correspond to approximately a half stroke length of a shock absorber stroke for an impact cushion assembly (e.g. , shock absorber assembly 100 of FIG. 1). In various embodiments, L2 can be between 35% and 65% of the length of the measurement pin 140. In various embodiments, the second flute profile 820 can be disposed on a fourth side 808 of the quadrilateral cross-section of the measurement pin 140. The fourth side 808 can be opposite the second side. Fourth side 808 may comprise a slot 842 in accordance with slot 822. In various embodiments, slots 812, 822, 832, 842 may all be the same.

[0042] In various embodiments, the first spline profile 810 can be configured to be effective over the entire travel range. In various embodiments, the second spline profile 820 can be configured to be effective from a fully extended stroke to approximately half a stroke. The combination of the first spline profile 810 and the second spline profile 820 used in combination provides greater cushioning as a function of stroke compared to using only the first spline profile 810 or only the second spline profile 820.

[0043] In various embodiments, with combined reference to FIGS. 6 and 8A-8B, slots 812, 822, 832, 842 can all be configured to interface with a restrictor portion 620 of the flow restrictor 600 when a flow restrictor 600 is in a fully deployed position in an orifice assembly main. For example, a fillet portion 814 of slot 812 may be configured to interface with column 622 of restrictor portion 620 of flow restrictor 600. Likewise, first convex surface 621 may be configured to interface with first wall 815 of slot 812 and second convex surface 623 of restrictor portion 620 of flow restrictor 600 may be configured to interface with second wall 816 of slot 812.

[0044] Referring now to FIGs. 9A and 9B, a portion of an impact pad assembly along a top view, in accordance with various embodiments, is illustrated. In various embodiments, orifice support tube 150 may further comprise a coupling end 152 disposed axially adjacent to the main orifice plate 180. The main orifice plate 180 may comprise an opening 910. The opening 910 may correspond to a shape of cross section of measuring pin 940 (eg a quadrilateral shape or similar). Gauge pin 940 may be disposed in opening 910 and configured to transfer torque from gauge pin 940 to main hole plate 180 in order to synchronize a main hole assembly (e.g., main hole assembly 160 of FIG. 3), according to various modalities. In various embodiments, measurement pin 940 may conform to measurement pin 140 of FIGs. 8A-8B.

[0045] In various embodiments, the coupling end 152 may comprise a clearance opening 151. The clearance opening 151 may be configured to receive the measuring pin 140 therethrough. Disposed radially outwardly of clearance opening 151, coupling end 152 may further comprise a first offset alignment opening 153. In various embodiments, coupling end 152 further comprises a second offset alignment opening 155 disposed approximately 180°. degrees of first offset alignment opening 153 in coupling end 152. Any number of offset alignment openings located at any radial position in coupling end 152 is within the scope of this disclosure.

[0046] In various embodiments, main orifice plate 180 may further comprise a first bypass opening 902 disposed radially outward from opening 910. In various embodiments, main orifice plate 180 may further comprise a second bypass opening 904 arranged at approximately 180 degrees from the first bypass opening 902. Any number of bypass openings located at any radial position in the main orifice plate 180 is within the scope of this disclosure. In various embodiments, the number of offset alignment openings in coupling end 152 corresponds to a series of offset openings in main orifice plate 180. In various embodiments, the orientation of offset alignment openings in coupling end 152 at relation to each other can correspond to the orientation of the bypass openings in the main orifice plate 180.

[0047] Referring now to FIG. 9A only, a closed bypass configuration of an impact cushion assembly 100 of FIG. 1 is illustrated according to various embodiments. The closed bypass configuration can occur when the first bypass opening 902 of the main orifice plate 180 is circumferentially offset with the first bypass alignment opening 153 of the coupling end 152.
Likewise, the second offset opening 904 of the main orifice plate 180 may be circumferentially offset with the second offset alignment opening 155 when in the closed offset configuration.

[0048] A multi-actor damping system can open and close the bypass openings 902, 904 depending on the angle of the actor. After rotating the main orifice plate 180 as shown in FIG. 9A, the bypass openings 902, 904 may be aligned with the bypass alignment openings 153, 155 of the coupling end 152 and opening the bypass openings 902, 904 as shown in FIG. 9B. As such, FIG. 9B depicts a closed bypass configuration of an impact cushion assembly, in accordance with various embodiments. Using bypass openings in this manner can provide various dampening actor configurations with or without the use of flow restrictors. In various embodiments, bypass openings 902, 904 can shift an entire damping curve up or down depending on whether they are in an open or closed configuration.

[0049] Control of the bypass area can also be beneficial with regard to percolation, which occurs from a restriction of the flow of gas and oil through the main orifice plate 180 when the hydraulic chamber is recharged after a train of landing has been stored for flight and then extended for landing.

[0050] Referring now to FIGs. 10A - 17B, the retraction of the first flow restrictor 162 and the second flow restrictor 164 along various angles of the actor is illustrated, in accordance with various embodiments. Referring now to FIGs. 10A and 10B, cross sections of a portion of an impact damper assembly having a first orientation (i.e., a first damping actor configuration corresponding to a first flow restrictor 162 and second flow restrictor 164 being deployed) are illustrated. , according to various modalities. In the first damping actor setup, the actor angle is approximately 0 degrees. In various embodiments, the actor angle is between -5 degrees and 5 degrees in the first damping actor setting.

[0051] In various embodiments, the restrictor portion 620 of the first flow restrictor 162 and the second flow restrictor 164 are each disposed in a slot (e.g., slot 822 of the second flute profile 820 for the first restrictor of flow restrictor 162 and slot 842 of the second spline profile 820 to the second flow restrictor 164). The restrictor portion 620 may at least partially contact a respective groove (e.g., the restrictor portion 620 of the first flow restrictor 162 may contact the groove 822 of the second spline profile 820 and the portion restrictor 620 of second flow restrictor 164 may contact groove 842 of second spline profile 820). A constraining angle can be defined around a centerline of opening 615. For example, a position of 0 degrees can be defined by a vector (eg, vector A) extending perpendicular from the centerline of opening 615 of each flow restrictor (e.g., opening 615 of first flow restrictor 162 and opening 615 of second flow restrictor 164) to a trailing end 629 of each flow restrictor (e.g., trailing end 629 of first flow restrictor flow 162 and aft end 629 of the second flow restrictor 164). In the first damping actor setting, the flow restrictor angle for each flow restrictor can be 0 degrees by definition (ie, the first damping setting defines a first orientation over which the restrictor angle is measured). In many embodiments, when the flow restrictor is fully deployed, the restrictor angle is 0 degrees by default.

[0052] Referring now to FIGs. 11A and 11B, cross sections of a portion of an impact damper assembly having a first orientation (i.e., an actor angle between a first damping actor configuration - e.g., a fully deployed flow restrictor) and a second damping actor configurations (eg, a fully retracted flow restrictor) are illustrated according to various modalities. In the first orientation, the actor's angle is approximately 22.5 degrees. In many modalities, the actor's angle is between 20 degrees and 25 degrees in the first orientation.

[0053] In various embodiments, the restrictor portion 620 of the first flow restrictor 162 and the second flow restrictor 164 each remain disposed in a slot (e.g., slot 822 of the second flute profile 820 for the first restrictor of flow restrictor 162 and slot 842 of the second spline profile 820 to the second flow restrictor 164). The restrictor portion 620 may at least partially contact a respective groove (e.g., the restrictor portion 620 of the first flow restrictor 162 may contact the groove 822 of the second spline profile 820 and the portion restrictor 620 of second flow restrictor 164 may contact groove 842 of second spline profile 820). In the first orientation, the restrictor angle for each flow restrictor can be approximately 0 degrees. In many embodiments, the flow restricting angle is between 0 degrees and 5 degrees in the first orientation.

[0054] With brief reference to FIGs. 6, 7 and 11A-B, in the first orientation, a protrusion of a flow restrictor may be near a first end of the guide ramp 710 (e.g., a protrusion 618 of the first flow restrictor 162 may be near a first end of guide ramp 710 of a first orbit cam 167. In various embodiments, main orifice plate 180 may further comprise a tongue 1102 disposed at a proximal end of main orifice plate 180 and extending in the radial direction. be received in slot 736 of the second orbit cam 169. As the measuring pin 140 is still rotated about its central axis, the measuring pin 140 applies torque to the main orifice plate 180. The measuring pin 140 can drive the rotation of the main orifice plate 180 while the second orbit cam 169 remains stationary. Its protrusion can be guided by guide ramp 710 and begin to retract its flow restrictor (by For example, the protrusion 618 of the first flow restrictor 162 may be guided by the guide ramp 710 of the first orbit cam 167).

[0055] Referring now to FIGs. 12A and 12B, cross sections of a portion of an impact damper assembly having a second orientation (i.e., an actor angle between the first orientation and a second dampening actor configuration - e.g., a fully retracted flow restrictor ) are illustrated, according to various modalities. In the second orientation, the actor's angle is approximately 45 degrees. In many modalities, the actor's angle is between 40 degrees and 50 degrees in the second orientation.

[0056] In various embodiments, the restrictor portion 620 of the first flow restrictor and the second flow restrictor 164 can be partially removed from the original groove of the first damping actor configuration and the first orientation (e.g., the second flow restrictor flow 164 may be disposed outside of slot 842 for the second flow restrictor 164 of FIG. 11B). In the second orientation, the restrictor angle for each flow restrictor can be approximately 14 degrees. In many embodiments, the restricting angle can be between 10 degrees and 19 degrees in the second orientation.

[0057] With brief reference to FIGs. 6, 7 and 12A-B, in the second orientation, a protrusion of a flow restrictor may be disposed a first axial distance from a proximal end 732 of a respective orbit cam in guide ramp 710 (e.g., a protrusion 618 of the second flow restrictor 164 may be an axial distance from the proximal end 732 of the second orbit cam 169 in guide ramp 710). As the protrusion 618 of the second flow restrictor 164 travels on the guide ramp 710, the head portion 610 of the second flow restrictor 164 rotates about the opening 615 of the second flow restrictor 164 and changes the angle of the flow restrictor as the second flow restrictor 164 begins to retract. As the measuring pin 140 is further rotated about its central axis, its protrusion may be guided by the guide ramp 710 and begin to retract the respective flow restrictor (e.g., protrusion 618 of the first flow restrictor 162 may be guided by guide ramp 710 of first orbit cam 167).

[0058] Referring now to FIGs. 13A and 13B, the cross-sections of a portion of an impact cushion assembly having a third orientation (i.e., an actor angle between the first and second orientations and a first and second configuration of the cushioning actor - e.g., a fully retracted flow restrictor) are illustrated, according to various modalities. In the third orientation, the actor's angle is approximately 67.5 degrees. In many modalities, the actor's angle is between 62.5 degrees and 72.5 degrees in the third orientation.

[0059] In various embodiments, the restrictor portion 620 of the first flow restrictor and the second flow restrictor 164 remain close to their respective slots compared to the first actor configuration, with the first orientation and with the second orientation (by example, slot 842 from second spline profile 820 to second flow restrictor 164). Restrictor portion 620 may be spaced from the respective slot (e.g., restrictor portion 620 of second flow restrictor 164 may be spaced from slot 842 of second spline profile 820). In the third orientation, the restrictor angle for each flow restrictor can be approximately 57 degrees. In various embodiments, the restricting angle can be between 52 degrees and 62 degrees in the third orientation.

[0060] With brief reference to FIGs. 6, 7 and 13A-B, in the third orientation, a protrusion of a flow restrictor may be disposed a second axial distance from a proximal end 732 of a respective orbit cam in guide ramp 710 (e.g., a protrusion 618 of the second flow restrictor 164 may be an axial distance from the proximal end 732 of the second orbit cam 169 in guide ramp 710). The second axial distance can be greater than the first axial distance in the second orientation. As the protrusion 618 of the second flow restrictor 164 travels on the guide ramp 710, the head portion 610 of the second flow restrictor 164 rotates about the opening 615 of the second flow restrictor 164 and changes the angle of the flow restrictor as the second flow restrictor 164 continues to retract. As the measuring pin 140 is still rotated about its central axis, the protrusion 618 may be guided by the guide ramp 710 and continues to retract the respective flow restrictor (e.g., the protrusion 618 of the first flow restrictor 162 may be guided by guide ramp 710 of first orbit cam 167).

[0061] Referring now to FIGs. 14A and 43B, cross sections of a portion of an impact cushion assembly having a second cushioning actor configuration (i.e., an orientation with fully retracted flow restrictors) are illustrated, in accordance with various embodiments. In the second actor damping setting, the actor angle is approximately 90 degrees. In many embodiments, the actor's angle is between 80 degrees and 100 degrees in the second actor damping setting. In the second damping actor configuration, the restrictor angle for each flow restrictor can be approximately 81 degrees. In many embodiments, the restricting angle can be between 76 degrees and 86 degrees in the third orientation.

[0062] With brief reference to FIGs. 6, 7 and 13A-B, in the second damping actor configuration, a protrusion of a flow restrictor may be disposed a third axial distance from a proximal end 732 of a respective orbit cam in guide ramp 710 (e.g., a protrusion 618 of the second flow restrictor 164 may be an axial distance from the proximal end 732 of the second orbit cam 169 on the guide ramp 710). The third axial distance can be greater than the first axial distance in the second orientation and the second axial distance in the third orientation. As the protrusion 618 of the second flow restrictor 164 travels on the guide ramp 710, the head portion 610 of the second flow restrictor 164 rotates about the opening 615 of the second flow restrictor 164 and changes the angle of the flow restrictor with the second flow restrictor 164 retracts fully as it rotates from the third orientation to the second damping actor setting. As the measuring pin 140 is still rotated about its central axis, the protrusion 618 can be guided by the guide ramp 710 and retracts the respective flow restrictor (for example, the protrusion 618 of the first flow restrictor 162 may be guided by the guide ramp 710 of first orbit cam 167).

[0063] Referring now to FIG. 15, a cross-section of a portion of an impact cushion assembly with the metering pin and main orifice plate hidden is illustrated, in accordance with various embodiments. In various embodiments, guide ramp 710 of orbit cam 700 extends axially away from proximal end 732 as it travels circumferentially away from first mating surface 702 and toward second mating surface 704 until a maximum axial distance is reached. D1 of the proximal end 732 before beginning to extend axially toward the proximal end 732 as it continues to extend circumferentially until it reaches the corresponding second surface 704.

[0064] Referring now to FIG. 16, an exploded view of a portion of a main port assembly 160, in accordance with various embodiments, is illustrated. In various embodiments, the orbit cams can have radial freedom along a line of motion while remaining synchronized with the outer support tube. This can be achieved by including four flat mating surfaces arranged approximately 90 degrees apart between various components. For example, the flat recess 724 of the first orbit cam 167 may interact with a first flat recess 1624 disposed in a radially inner surface of the main orifice plate retainer 184. Likewise, the flat recess 724 of the second orbit cam 169 may interact with a second flat recess 1626 disposed radially opposite the first flat recess 1624.

[0065] The main orifice plate retainer 184 may further comprise a first flat mating surface 1634 disposed on a radially outer surface of the main orifice plate retainer 184 and a second flat mating surface disposed opposite the first flat mating surface . Each flat mating surface of the main hole plate retainer 184 may mate with a corresponding flat mating surface of the orifice support tube 150. For example, the second flat mating surface may mate with a second flat mating surface 1642 disposed. on a radially inner surface of the orifice support tube 150. Similarly, the first flat mating surface 1634 may coincide with a first flat mating surface disposed on a radially inner surface of the orifice support tube 150, the first surface mating surface disposed radially opposite the second flat mating surface 1642.

[0066] The flat mating surface allows the metering pin, the main orifice plate 180, the first orbit cam 167 and the second orbit cam 169 to radially translate together, while maintaining the first orbit cam 167 and the second orbit cam 169 aligned with orifice support tube 150 in terms of actor angle. In various embodiments, the main orifice assembly 160 is configured to allow the first orbit cam 167 and the second orbit cam 169 to be disposed radially into the orifice plate assembly 182 and to slide relative to the orifice plate assembly. main in linear directions, preventing rotation of the first orbit cam 167 and the second orbit cam 169.

[0067] The main orifice assembly 160 can be configured to allow axial displacement of the main orifice plate 180 during operation of a respective shock absorber assembly. For example, the main orifice plate assembly 182 can mount the main orifice plate retainer 184, first orbit cam 167, second orbit cam 169, and main orifice plate 180 within coupling end 152 of the support tube. hole 150 loosely in the axial direction. As such, main orifice plate 180 can be configured to move axially within coupling end 152 and/or pivot about a centerline of a respective measurement pin.

[0068] Referring now to FIGs. 17A and 17B, a main orifice assembly 160 during operation of an impact cushion assembly, in accordance with various embodiments, is illustrated. FIG. 17A illustrates oil flow during shock compression and FIG. 17B illustrates oil flow during damper extension, in accordance with various embodiments. Coupling end 152 may further comprise a plurality of bypass flow openings 1702.

[0069] With reference to FIGs. 1 and 17A, during compression of the bracket, oil flows from the oil chamber 134 through the main orifice assembly 160 and into the orifice support tube 150. During compression of the bracket, the main orifice plate 180 can be configured to axially move the coupling end 152 of the orifice support tube 150 and contact an axial surface 1704 of the coupling end 152. Upon contacting the axial surface 1704 of the coupling end 152, the main orifice plate 180 may act as a seal between the oil flow between the oil chamber 134 and the orifice support tube 150 and the plurality of bypass flow openings 1702.

[0070] Referring now to FIGs. 1 and 17B, during extension of the bracket, oil flows from the orifice support tube 150 through the main orifice assembly 160 and into the oil chamber 134. The main orifice plate 180 can be configured to separate axially from the axial surface 1704 of coupling end 152. In this regard, a bypass flow path may be created between the axial surface 1704 and an axial surface 1706 of the main orifice plate 180 through the plurality of bypass flow openings 1702. The separation between the axial surface 1704 of the coupling end 152 and the axial surface 1706 of the main orifice plate can be separated by a gap G1. The G1 gap can be a design consideration and/or can be varied based on the damping actor angle to find a desired damping curve for a damping actor configuration. For example, G1 can vary for a given 180 main orifice plate as a function of circumferential position, or G1 can be fixed and varied based on initial design considerations. In a design where G1 varies as a function of circumferential position, a G1 gap can match a damping actor configuration to provide higher or lower damping. For example, a larger G1 might correspond to a smaller damping curve, while a smaller G1 might correspond to a larger damping curve.

[0071] Referring now to FIG. 18, a main orifice assembly 160, in accordance with various embodiments, is illustrated. Main hole assembly 160 may further comprise first spring 192 coupled to first flow restrictor 162 and second spring 194 coupled to second flow restrictor 164. Each spring 192, 194 may be any spring known in the art, such as a spring of mooring ring or similar. Each flow restrictor may further comprise a spring pocket defined at least partially by first recess 626 and second recess 619 as defined in FIG. 6. For example, the first flow restrictor 162 may comprise a spring pocket 1802 configured to house the first spring 192.

[0072] In various embodiments, each spring deflection curve can be relatively flat (ie, the curve can stabilize at a limit displacement). The spring force of each spring can be minimized, resulting in reduced torque for changing damping actor settings and reducing the restriction of flow restrictors for refilling hydraulic chamber oil when the damper is extending.

[0073] Referring now to FIG. 19, a main orifice plate assembly 1980 and a metering pin 140, in accordance with various embodiments, are illustrated. In various embodiments, the orifice plate assembly 1980 may comprise a metering plate 180, a first flow restrictor 162 coupled to the main orifice plate 180, and a second flow restrictor 164 coupled to the main orifice plate 180. In various embodiments , a first and a second cam in the plurality of cams may be coupled to a respective flow restrictor. For example, first boss 1902 and second boss 1904 can define a flange yoke. A head portion 610 of the first flow restrictor 162 may be disposed on the flange fork. With combined reference to Figures 6 and 19, a pin may be disposed through a first opening 1912 of first boss 1902 through opening 615 of head portion 610 and through a corresponding second opening of second boss 1904. a fulcrum for the first flow restrictor to rotate.

[0074] In various embodiments, each lug in the plurality of lugs may extend axially beyond the head portion 610 of a respective flow restrictor. In this regard, each ledge in the plurality of ledges 186 can restrict flow around the respective flow restrictor when positioned to the maximum flute depth. A consistent level of leakage can be established based on a distance between each lug in the plurality of lugs 186 and the measurement pin 140.

[0075] Referring now to FIG. 20, a portion of an impact cushion assembly 2000 including a main orifice assembly 2060 from a bottom view, in accordance with various embodiments, is illustrated. "Bottom view", as referred to herein, is a view looking from the damping actor selector 170 towards the orifice support tube 150 in FIG. 1. In various embodiments, the 2000 shock absorber assembly is for a steerable gear.

[0076] Referring again to FIG. 1, a "steering angle" as defined herein is a relative clock angle between the damper cylinder 110 and the damper piston 120. A "dampening actor selector angle (DAS)" as defined in this document , is a relative clock angle between measuring pin 140 and damper piston 120. In various embodiments, damping actor selector 170 rotates measuring pin 140 with respect to damper piston 120 and the direction rotates the piston of the damper 120 relative to the damper cylinder 110. As such, the actor angle can be the sum of the steering angle and the DAS angle.

[0077] As a steerable gear, the steering angle of the 2000 shock absorber assembly can be approximately 360 degrees. However, steering during a first damping actor 2002 setup may be limited to a first steering range and/or steering during a second damping actor 2004 setup may be limited to a second steering range. The steering ranges of each damping actor configuration can be a design choice.

[0078] Referring again to FIG. 20, a 2010 actor angle can be set between a 2002 first damping actor setting and a 2004 damping second actor setting based on a direction range of each damping actor setting. For example, with reference to FIGs. 7 and 20, if a 2002 first damping actor configuration has 74 degrees of direction (-37 degrees to 37 degrees from a neutral position), and the 2004 second damping actor configuration has 24 degrees of direction (-37 degrees to 37 degrees from a neutral position), and the neutral positions of the 2002 first damping actor configuration and the 2004 second damping actor configuration are 90 degrees apart (ie, an actor angle of 90 degrees), a guide ramp 710 of a 700 orbital cam can span 41 degrees maximum (eg 90 degrees - 12 degrees - 37 degrees). Furthermore, in this configuration, the start of the guide ramp can be at least 37 degrees from a first mating surface 702 and the maximum axial distance D1 can occur at a maximum of 88 degrees. In addition, the maximum axial distance D1 of the guide ramp can span at least 24 degrees, corresponding to at least the steering angle while in the second damping actor configuration.

[0079] With reference to FIGs. 1 and 20, to change the damping actor setting (i.e., from the first damping actor 2002 setting to the second damping actor 2004 setting), the damping actor selector 170 can rotate the measuring pin in the direction clockwise or counterclockwise by the actor's angle (for example, 90 degrees in FIG. 20). In various embodiments, the first damping actor 2002 configuration may correspond with a first flow restrictor 162 and second flow restrictor 164 being fully retracted. In various embodiments, the second configuration of damping actor 2004 may correspond with the first flow restrictor 162 and the second flow restrictor 164 being fully deployed. In various embodiments, the first damping actor configuration may correspond to a damping curve configured for landing an aircraft. In various embodiments, the configuration of the second damping actor can correspond to an aircraft catapult.

[0080] Referring now to FIG. 21, a portion of an impact cushion assembly 2100 including a main orifice assembly 2160 from a bottom view, in accordance with various embodiments, is illustrated. In various embodiments, the shock absorber assembly 2100 is for a non-steerable gear. In various embodiments, a non-steering gear can be configured to have multiple damping actor configurations. For example, an impact cushion assembly 2100 for a non-steering gear may comprise a first cushioning actor configuration 2102, a second cushioning actor configuration 2104, a third cushioning actor configuration 2106 and/or a fourth cushioning actor configuration 2108 damping actor.

[0081] In various embodiments, the first configuration of damping actor 2102 can correspond to a damping curve designed for a percolation event. Percolation occurs when restricting the flow of gas and oil through the main orifice assembly 2160 when the hydraulic chamber is recharged after a landing gear has been retracted for flight. In the first configuration of the damping actor 2102, the main orifice assembly 2160 can open a large flow area between the hydraulic and gas chambers in order to facilitate a gas/oil migration between the chambers. This can allow an aircraft to land safely in a shorter amount of time after downshifting.

[0082] In various embodiments, the configuration of the second damping actor 2104 can correspond to a damping curve designed for conventional take-off and landing (CTOL). In various embodiments, the third configuration of damping actor 2106 can correspond to a damping curve designed for short takeoff and vertical landing (STOVL). The third configuration of damping actor 2106 can be adjusted for vertical landings. For example, the third damping setting may provide greater energy absorption as spin-up and spring back effects may have less influence. The third damping actor setting can also match a damping curve designed for rough terrain.

[0083] In various embodiments, the fourth configuration of the damping actor 2108 may correspond to a damping curve designed for taxiing an aircraft. The fourth damping actor setting can be optimized for displacement quality or similar.

[0084] In various embodiments and with further reference to FIG. 22, a schematic block diagram of a control system 2200 for the damping actor selector 2270 is illustrated. The control system 2200 includes a controller 2202 in electronic communication with a launchpad lock 2204 and a sensor 2206. In various embodiments, the controller 2202 can be integrated with computer systems on board the aircraft. In various embodiments, controller 2202 may be configured as a central network element or hub to access various systems, engines, and components of control system 2200. Controller 2202 may comprise a network, computer-based system, and/or software components configured to provide an access point to various systems, engines, and components of control system 2200. In various embodiments, controller 2202 may comprise a processor. In various embodiments, controller 2202 can be implemented on a single processor. In various embodiments, controller 2202 can be implemented as and can include one or more processors and/or one or more tangible, non-transient memories and be capable of implementing logic. Each processor can be a general purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic device, discrete gate, or computer logic. transistor, discrete hardware components, or any combination of these. Controller 2202 may comprise a processor configured to implement various logical operations in response to the execution of instructions, for example, instructions stored on a non-transient, tangible, computer-readable medium configured to communicate with controller 2202.

[0085] System program instructions and/or controller instructions may be loaded into a computer-readable non-transient tangible medium with instructions stored therein which, in response to execution by a controller, cause the controller to perform various operations. The term “non-transient” is to be understood as removing only the propagation of transient signals per se from the scope of the claim and does not waive the rights of all standard computer-readable media that are not only propagating transient signals per se. In other words, the meaning of the term "computer-readable non-transient media" and "computer-readable non-transient storage media" is to be interpreted as excluding only those types of computer-readable transient media found in In Re Nuijten that come out of scope of subject matter patentable under 35 USC § 101.

[0086] In various embodiments, the controller 2202 can be in electronic communication with the launchpad lock 2204 and/or sensor 2206. When the launchpad lock 2204 is on, a switch can be closed and the launchpad lock launcher 2204 can be engaged/locked. When the launchpad lock 2204 is off, a switch can be closed and the aircraft can be configured for a catapult launch. Sensor 2206 may comprise any load cell known in the art, such as a compression load cell or the like. Sensor 2206 can be configured to measure a weight on wheels and indicate if the aircraft is on the ground. Sensor 2206 and launch bar latch 2204 can be configured to transmit signals to controller 602, thereby providing a phase of flight for controller 2202.

[0087] In various embodiments, the controller 2202 may receive a catapult command to extend a launch bar latch 2204 to a deck in order to configure the aircraft for a catapult launch. In response to the catapult command, the controller 2602 may command the damping actor selector 2270 to transition from a first damping actor configuration to a second damping actor configuration. In response, damping actor selector 2270 may rotate meter pin 140 and main orifice plate 180 in a first direction about a central axis of meter pin 140 and/or deploy a first flow restrictor 162 and /or a second flow restrictor 164. In various embodiments, when sensor 2206 no longer measures a weight on the aircraft wheels, controller 2202 may command dampening actor selector 2270 to transition back from the second configuration of damping actor for the first damping actor setting. In this regard, the damping actor selector 2270 can rotate the metering pin 140 and the main orifice plate 180 in a second direction around the central axis of the metering pin 140 and/or retract the first flow restrictor 162 and /or the second flow restrictor 164. The second direction may be opposite the first direction.

[0088] In various embodiments, the launch bar lock 2204 may re-engage after catapult launch. In response, if the sensor still measures a weight on the wheels when the launch bar latch 2204 re-engages a latch, the controller 2202 may command the damping actor selector 2270 to transition back from the second damping actor configuration to the first damping actor configuration. In this regard, the damping actor selector 2270 can rotate the metering pin 140 and the main orifice plate 180 in a second direction around the central axis of the metering pin 140 and/or retract the first flow restrictor 162 and /or the second flow restrictor 164. The second direction may be opposite the first direction.

[0089] In various embodiments, controller 2202 may command launch bar latch 2204 to re-engage after catapult launch. In response, if the sensor still measures a weight on wheels, controller 2202 may command damping actor selector 2270 to transition back from the second damping actor configuration to the first damping actor configuration. In this regard, the damping actor selector 2270 can rotate the metering pin 140 and the main orifice plate 180 in a second direction around the central axis of the metering pin 140 and/or retract the first flow restrictor 162 and /or the second flow restrictor 164. The second direction may be opposite the first direction.

[0090] Referring now to FIG. 23, a method 2300 of defining an actor angle of a multi-actor damping system is illustrated, in accordance with various embodiments. The method comprises rotating, by means of a damping actor selector, a measurement pin about a central axis of the measurement pin in a first direction from a standard position (step 2302). The default position can correspond to a first damping actor setting. The first configuration of the damping actor may comprise a damping curve configured for conventional landing or the like. The damping actor selector may be in accordance with the damping actor selector 170. The method may further comprise defining, by means of the damping actor selector, a first actor angle of the multi-actor damping system (step 2304). The first actor angle can correspond to a second damping actor configuration. The second configuration of the damping actor may comprise a damping curve configured for catapult launch or the like.

[0091] The method may further comprise rotating, by means of the damping actor selector, the measuring pin around the central axis of the measuring pin in a second direction (step 2306). In many modalities, the second direction may be the same as the first direction in a multi-actor damping system where with more than two actor damping configurations (eg, for a non-steerable landing gear). In many modalities, the second direction may be opposite the first direction in a multi-actor damping system, where there are only two actor damping configurations (eg, for an airship landing gear). The method may further comprise defining a second actor angle (step 2308). The second actor angle can be different from the first actor angle. The second actor angle can correspond to the first damping actor configuration or a third damping actor configuration. The second actor angle can be the first negative actor angle in an airship landing gear system. The third configuration of the damping actor may comprise a damping curve configured for short takeoff and vertical landing, taxi or the like.

[0092] Benefits, other advantages and solutions to problems have been described in this document in relation to specific modalities. Additionally, the connecting lines shown in the various figures included in this document are intended to represent examples of functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical links may be present in a practical system. However, benefits, advantages, solutions to problems and any elements that could cause any benefit, advantage, or solution to occur or become more pronounced will not be construed as critical, necessary or essential features or elements of the disclosure.

[0093] The scope of the disclosure is therefore limited by nothing more than the appended claims, in which reference to a singular element is not intended to mean "one and only one" unless explicitly stated, but rather to rather, "one or more". It should be understood that, unless specifically indicated otherwise, references to "a," "an," and/or "a" may include one or more than one and that a reference to a singular item may also include the item in the plural. All ranges and reason limits disclosed in this document may be combined.

[0094] Furthermore, when a phrase similar to "at least one of A, B, or C" is used in the claims, the expression is intended to be interpreted as meaning that A alone may be present in a modality, B alone can be present in one modality, C alone can be present in one modality, or that any combination of elements A, B and C can be present in a single modality; for example, A and B, A and C, B and C or A and B and C.

[0095] The steps referred to in any of the method or process descriptions can be performed in any order and are not necessarily limited to the order presented. Furthermore, any reference to the singular includes plural modalities and any reference to more than one component or step may include a singular modality or step. Elements and steps in the figures are illustrated for simplicity and clarity and are not necessarily provided in any particular sequence. For example, steps that can be performed simultaneously or in a different order are illustrated in the figures to help improve understanding of the embodiments of the present disclosure.

[0096] Any reference to attachment, attachment, attachment or the like may include other possible permanent, removable, temporary, partial and/or complete attachment option. Additionally, any reference to lack of contact (or similar phrases) may also include reduced contact or minimal contact. Surface shading lines can be used in figures to represent different parts or areas, but not necessarily to represent the same materials or different materials. In some cases, reference coordinates can be specific to each figure.

[0097] Systems, methods and apparatus are provided in this document. In the detailed description of this document, references to “a modality”, “a modality”, “multiple modalities”, etc., indicate that the described modality may include a particular feature, structure, or characteristic, but every modality may not necessarily include the particular feature, structure, or feature. Furthermore, such phrases do not necessarily refer to the same modality. Additionally, when a particular feature, structure, or feature is described in connection with a modality, it is claimed that those skilled in the art are known to presuppose that feature, structure, or feature in connection with other explicitly described modalities or not. After reading the descriptive report, it will be evident to those versed in the relevant technique(s) how to implement disclosure in alternative modalities.

[0098] Furthermore, no element, component, or method step in this disclosure is intended to be dedicated to the public, regardless of whether the element, component, or method step is expressly recited in the claims. No element of claim is intended to appeal to 35 U.S.C. 112(f) unless the element is expressly recited using the phrase "means to." As used in this document, the terms "comprises", "comprising" or any other variation thereof are intended to cover a non-exclusive inclusion, such that a process, method, article or apparatus comprising a list of elements does not include elements only, but may include other elements that are not expressly listed or are inherent in such process, method, article or apparatus.

Claims (15)

Method for changing a damping curve of an impact damper assembly, characterized by the fact that it comprises:
rotating, by means of a damping actor selector, a main orifice plate from a standard position about a centerline of a measuring pin in a first direction, the standard position corresponding to a first damping actor configuration;
adjust, via the damping actor selector, a first actor angle corresponding to a second damping actor setting. A method according to claim 1, characterized in that the first damping actor configuration includes a first damping curve, wherein the second damping actor configuration includes a second damping curve and wherein the first damping curve and the second damping curve are different. Method according to claim 2, characterized in that the first damping curve is for conventional landing of an aircraft. Method according to claim 3, characterized in that the second damping curve is for a catapult launch of the aircraft. Method according to claim 1, characterized in that it further comprises rotating, by means of the damping actor selector, the measuring pin from the first actor angle to a second actor angle. Method according to claim 5, characterized in that the second angle of the actor corresponds to the first configuration of the damping actor. Method according to claim 5, characterized in that the second actor angle corresponds to a third damping configuration. Method according to claim 7, characterized in that the first damping actor configuration includes a first damping curve, wherein the second damping actor configuration includes a second damping curve, wherein the third damping configuration includes a third damping curve, where the first damping curve is different from the second damping curve, where the second damping curve is different from the first damping curve, and where the first damping curve is different from the third damping curve. damping. Method according to claim 1, characterized in that the first actor angle is a relative clock angle between the measuring pin and a support cylinder. Method for selecting a damping configuration of an impact damper assembly for an aircraft, characterized by the fact that it comprises:
sending, by a controller, a catapult launch command to a launch bar lock and a damping actor selector;
extending, by the controller, the launch bar latch to an aircraft deck to configure the aircraft for a catapult launch; and
transitioning, via the controller, the damping actor selector from a first damping actor configuration to a second damping actor configuration in response to the catapult launch command. Method according to claim 10, characterized in that the first damping actor configuration corresponds to a first damping curve, wherein the second damping actor configuration corresponds to a second damping actor curve and in which the first damping curve and second damping actor curve are different. Method according to claim 10, characterized in that the transition of the damping actor selector from the first damping actor configuration to the second damping actor configuration further comprises defining an actor angle, wherein the actor angle is a relative clock angle between a measuring pin and a support cylinder, preferably further comprising transitioning, via the controller, the damping actor selector from the second damping actor configuration to the first damping actor configuration. damping in response to receiving a signal from a sensor that a wheel is not under load, preferably further comprising sending, by the controller, a re-engagement command to the launch bar lock and damping selector; and transitioning, via the controller, the damping actor selector from the second damping actor configuration to the first damping actor configuration in response to the re-engage command. Impact damper assembly, characterized by the fact that it comprises:
a support cylinder including a primary chamber;
a support piston, the support cylinder configured to receive the support piston;
an orifice support tube positioned within the primary chamber of the support cylinder;
a main orifice assembly disposed within the orifice support tube, the main orifice assembly including a main orifice plate;
a measuring pin positioned within the primary chamber, the measuring pin defining an axis; and
a dampening actor selector operatively coupled to the main orifice plate, the damping actor selector configured to rotate the main orifice plate and transition the shock absorber assembly from a first damping actor configuration to a second configuration of damping actor. Impact damper assembly according to claim 13, characterized in that the damping actor selector comprises hydraulic actuation or pneumatic actuation, preferably the damping actor selector comprises at least one of an electric stepper or a servo motor, preferably the first damping actor configuration includes a first damping curve, wherein the second damping actor configuration includes a second damping curve, and wherein the first damping curve is different from the second damping curve. Impact damper assembly according to claim 13, characterized in that the damping actor selector comprises a piston head coupled to the measuring pin, preferably the measuring pin rotates in response to the moving piston head linearly along the axis.

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